EP2144002A2 - Manchon avec ouvertures d'air pour le refroidissement d'un conduit de fumées - Google Patents
Manchon avec ouvertures d'air pour le refroidissement d'un conduit de fumées Download PDFInfo
- Publication number
- EP2144002A2 EP2144002A2 EP09250781A EP09250781A EP2144002A2 EP 2144002 A2 EP2144002 A2 EP 2144002A2 EP 09250781 A EP09250781 A EP 09250781A EP 09250781 A EP09250781 A EP 09250781A EP 2144002 A2 EP2144002 A2 EP 2144002A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- flow sleeve
- combustion
- holes
- tabs
- ring
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
- F23R3/48—Flame tube interconnectors, e.g. cross-over tubes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
Definitions
- the present invention relates to a flow sleeve for controlling cooling airflow to an outer periphery of a combustion liner in a gas turbine engine.
- Gas turbine engines typically include a compressor section that compresses air and delivers it downstream into a combustion section. The air is mixed with fuel in the combustion section and burned. Products of this combustion pass downstream towards a turbine section, to drive turbine rotors.
- a combustion sleeve directs the products of combustion from the combustion section downstream toward the turbine rotors.
- the combustion liner becomes quite hot from the products of combustion.
- a part called a flow sleeve is mounted between an outer housing and the combustion liner, and provided with a plurality of openings. Cooling air is provided radially outwardly of the flow sleeve, and is directed through the holes at the outer periphery of the combustion liner. In this way, the combustion liner is cooled.
- a plurality of tubular members extend about the holes, and from an inner periphery, to form conduits for controlling the direction in which the air is moved against the combustion liner.
- the tubular members add expense, and are complex to manufacture.
- the present invention discloses in one aspect a combustion liner to receive products of combustion in a gas turbine engine, and deliver the products of combustion downstream toward a turbine rotor.
- An outer housing is positioned radially outwardly of the combustion liner.
- a flow sleeve is positioned radially intermediate the outer housing and the combustion liner.
- the flow sleeve defines a chamber, radially outwardly of the flow sleeve, for receiving cooling air.
- a plurality of holes extend through the flow sleeve to deliver cooling air against an outer periphery of the combustion liner.
- a plurality of tabs are associated with at least some of the holes in the flow sleeve, and are positioned to extend radially inwardly on a downstream side of the holes.
- the tabs control the air flow direction but are less expensive than the prior art.
- a combustion duct 20 for use in a gas turbine engine is illustrated in Figure 1 .
- An outer housing 22 connects to a downstream duct 24 leading to a turbine section (not shown).
- Outer housing 22 also surrounds a combustion liner 31.
- Combustion liner 31 receives products of combustion X from combustion section 18 and delivers them downstream into duct 24.
- a flow sleeve 32 is positioned radially between the outer housing 22 and the combustion liner 31.
- a chamber 30 between the flow sleeve 32 and the outer housing 22 receives cooling air, such as from an upstream compressor (not shown). Holes 34 are formed through the flow sleeve 32. Air passes from the chamber 30 through the holes 34, and against the outer periphery of the combustion liner 31.
- tab ring 36 has a cylindrical base 38, and a plurality of tabs 40. Further, the base 38 includes holes 37 to be aligned with the last row of holes 35. As can be appreciated from Figure 2 , the tabs 40 do not extend over more than 180° defined about an axis extending through the holes 35. That is, tabs 40 are only on the downstream side of the holes 35. More specifically, as can be appreciated, the tabs 40 extend across less than 90°, and are generally formed to be tangent to an outer periphery of the hole at an upstream side.
- the tab 36 ring as disclosed extends over an entire 360° range about a central axis Z of the flow sleeve 32.
- the tab ring 36 may extend for less than 360°, but in embodiments, extends for at least 270° about the axis. Again, in the disclosed embodiment, the tab ring 36 does extend for 360° and is a complete ring.
- the tabs 40 and base 38 are formed as a single piece in a disclosed embodiment.
- tabs 40 extend radially inwardly from the base 38.
- Figure 4 shows the tab 40 extending inwardly from base 38, and positioned inwardly of the flow sleeve 32.
- the tabs 40 being aligned with the outer row of holes 35 shields cooling air from downstream cross-flow. Instead, cooling air from the holes 35 flows to an outer periphery of the combustion liner 31. Further, since the tabs 40 are only on a downstream side of the holes 35, and the base 38 does not extend as far radially inwardly as does the tab 40, the air is urged to flow back upstream, through the space 39 provided by the base 38. There will be a greater resistance to downstream flow due to the tab 40.
- the tab ring 36 can be said to have an upstream side and a downstream side, and tabs 40 are at the downstream side.
- this description allows for a portion of the base to extend on a downstream side of the tabs 40. That is, the tabs 40 need not be at an extreme edge of the ring 36, and can still be said to be at the downstream side.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/169,994 US8109099B2 (en) | 2008-07-09 | 2008-07-09 | Flow sleeve with tabbed direct combustion liner cooling air |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2144002A2 true EP2144002A2 (fr) | 2010-01-13 |
EP2144002A3 EP2144002A3 (fr) | 2013-03-20 |
EP2144002B1 EP2144002B1 (fr) | 2016-09-14 |
Family
ID=40578819
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09250781.3A Ceased EP2144002B1 (fr) | 2008-07-09 | 2009-03-20 | Manchon avec ouvertures d'air pour le refroidissement d'un conduit de fumées |
Country Status (2)
Country | Link |
---|---|
US (1) | US8109099B2 (fr) |
EP (1) | EP2144002B1 (fr) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9328925B2 (en) * | 2012-11-15 | 2016-05-03 | General Electric Company | Cross-fire tube purging arrangement and method of purging a cross-fire tube |
US11371701B1 (en) | 2021-02-03 | 2022-06-28 | General Electric Company | Combustor for a gas turbine engine |
US11885495B2 (en) | 2021-06-07 | 2024-01-30 | General Electric Company | Combustor for a gas turbine engine including a liner having a looped feature |
US11959643B2 (en) | 2021-06-07 | 2024-04-16 | General Electric Company | Combustor for a gas turbine engine |
US12085283B2 (en) | 2021-06-07 | 2024-09-10 | General Electric Company | Combustor for a gas turbine engine |
US11774098B2 (en) | 2021-06-07 | 2023-10-03 | General Electric Company | Combustor for a gas turbine engine |
US11920790B2 (en) * | 2021-11-03 | 2024-03-05 | General Electric Company | Wavy annular dilution slots for lower emissions |
US11747018B2 (en) | 2022-01-05 | 2023-09-05 | General Electric Company | Combustor with dilution openings |
CN116557910A (zh) | 2022-01-27 | 2023-08-08 | 通用电气公司 | 具有交替稀释栅的燃烧器 |
US12018839B2 (en) | 2022-10-20 | 2024-06-25 | General Electric Company | Gas turbine engine combustor with dilution passages |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6122917A (en) | 1997-06-25 | 2000-09-26 | Alstom Gas Turbines Limited | High efficiency heat transfer structure |
US6484505B1 (en) | 2000-02-25 | 2002-11-26 | General Electric Company | Combustor liner cooling thimbles and related method |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4184326A (en) * | 1975-12-05 | 1980-01-22 | United Technologies Corporation | Louver construction for liner of gas turbine engine combustor |
US4380906A (en) * | 1981-01-22 | 1983-04-26 | United Technologies Corporation | Combustion liner cooling scheme |
US4719748A (en) * | 1985-05-14 | 1988-01-19 | General Electric Company | Impingement cooled transition duct |
JPH0752014B2 (ja) * | 1986-03-20 | 1995-06-05 | 株式会社日立製作所 | ガスタ−ビン燃焼器 |
US4848081A (en) * | 1988-05-31 | 1989-07-18 | United Technologies Corporation | Cooling means for augmentor liner |
US5461866A (en) * | 1994-12-15 | 1995-10-31 | United Technologies Corporation | Gas turbine engine combustion liner float wall cooling arrangement |
GB9505067D0 (en) * | 1995-03-14 | 1995-05-03 | Europ Gas Turbines Ltd | Combustor and operating method for gas or liquid-fuelled turbine |
US5749229A (en) * | 1995-10-13 | 1998-05-12 | General Electric Company | Thermal spreading combustor liner |
US6000908A (en) * | 1996-11-05 | 1999-12-14 | General Electric Company | Cooling for double-wall structures |
US7010921B2 (en) * | 2004-06-01 | 2006-03-14 | General Electric Company | Method and apparatus for cooling combustor liner and transition piece of a gas turbine |
US7900459B2 (en) * | 2004-12-29 | 2011-03-08 | United Technologies Corporation | Inner plenum dual wall liner |
US7311175B2 (en) * | 2005-08-10 | 2007-12-25 | United Technologies Corporation | Acoustic liner with bypass cooling |
-
2008
- 2008-07-09 US US12/169,994 patent/US8109099B2/en not_active Expired - Fee Related
-
2009
- 2009-03-20 EP EP09250781.3A patent/EP2144002B1/fr not_active Ceased
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6122917A (en) | 1997-06-25 | 2000-09-26 | Alstom Gas Turbines Limited | High efficiency heat transfer structure |
US6484505B1 (en) | 2000-02-25 | 2002-11-26 | General Electric Company | Combustor liner cooling thimbles and related method |
Also Published As
Publication number | Publication date |
---|---|
US8109099B2 (en) | 2012-02-07 |
US20100005805A1 (en) | 2010-01-14 |
EP2144002A3 (fr) | 2013-03-20 |
EP2144002B1 (fr) | 2016-09-14 |
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